Method and apparatus for forming a composite fuselage structure

ABSTRACT

A method and apparatus for tacking and trimming a thermoplastic tow. A thermoplastic tow is received from a braiding system over a braided structure on a surface. The thermoplastic tow is tack welded to the braided structure. A portion of the thermoplastic tow is trimmed to thereby trim the thermoplastic tow received over the braided structure.

FIELD

This disclosure generally relates to composite manufacturing and, moreparticularly, to methods and apparatuses for fabricating a compositefuselage structure by integrating a fuselage skin and fuselage stringerscomprised of overbraided material.

BACKGROUND

Different types of aircraft structures may be fabricated using compositematerials. Currently, many aircraft structures are formed usingthermoset composite materials. However, using thermoset compositematerials (e.g., thermoset resin) may be more challenging than desiredwhen fabricating larger sized and shaped aircraft structures, such asfuselage barrel sections. Further, the process involved in usingthermoset composite materials for such structures may be moretime-consuming and costly than desired.

For example, the process of fabricating a fuselage barrel section usinga thermoset composite material may involve more facility resources(e.g., facility equipment) and tooling than desired. Additionally,traditional methods involving the use of an autoclave to cure a fuselagebarrel structure comprised of thermoset composite material may be slowerthan desired with respect to production rate requirements. Meeting suchproduction rate requirements may require a more significant investmentin capital, equipment, facility resources, or a combination thereof thandesired.

Therefore, it would be desirable to have a method and apparatus thattakes into account at least some of the issues discussed above, as wellas other possible issues.

SUMMARY

In one illustrative example, a tow tacking and trimming apparatuscomprises a tacking-trimming system and a support system. Thetacking-trimming system is for use in tacking and trimming athermoplastic tow to a braided structure. The tacking-trimming system isattached to the support system. The support system is sized and shapedto operatively place the tacking-trimming system relative to acylindrical thermoplastic stackup.

In another illustrative example, a method for tacking and trimming athermoplastic tow is provided. A thermoplastic tow is received from abraiding system over a braided structure on a surface. The thermoplastictow is tack welded to the braided structure. A portion of thethermoplastic tow is trimmed to thereby trim the thermoplastic towreceived over the braided structure.

In yet another illustrative example, a method for tacking and trimming athermoplastic tow is provided. The thermoplastic tow received from abraiding system is laid up over a braided structure on a surface. Thethermoplastic tow received from the braiding system is tack welded tothe braided structure. The thermoplastic tow is trimmed by applyinglaser energy to a portion of the thermoplastic tow.

In still yet another illustrative example, a tacking-trimming setupcomprises a support ring, a tacking-trimming system, and a conductivecomponent. The support ring is sized and shaped to fully surround asurface that is circumferential. The tacking-trimming system is securedto the support ring for use in tacking a thermoplastic tow to a braidedstructure. The tacking-trimming system comprises a tack welder and atrimmer. The tack welder is secured to a portion of the support ring,wherein the tack welder is resistively heated. The trimmer is secured toa portion of the support ring, wherein the trimmer uses laser energy totrim the thermoplastic tow. The conductive component is positionedbetween the braided structure and the thermoplastic tow.

The features and functions can be achieved independently in variousembodiments of the present disclosure or may be combined in yet otherembodiments in which further details can be seen with reference to thefollowing description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the example embodimentsare set forth in the appended claims. The example embodiments, however,as well as a preferred mode of use, further objectives and featuresthereof, will best be understood by reference to the following detaileddescription of an example embodiment of the present disclosure when readin conjunction with the accompanying drawings.

FIG. 1 is a block diagram of a manufacturing environment in accordancewith an example embodiment.

FIG. 2 is a more detailed illustration of a stackup in accordance withan example embodiment.

FIG. 3A is an illustration of an isometric view of a consolidation setupin accordance with an example embodiment.

FIG. 3B is an illustration of a cross-sectional view of theconsolidation setup from FIG. 3A in accordance with an exampleembodiment.

FIG. 4 is an illustration of a portion of the inner tooling from FIG. 3taken between lines 4-4 in FIG. 3 in accordance with an exampleembodiment.

FIG. 5 is an illustration of cauls added to the stackup from FIG. 4 inaccordance with an example embodiment.

FIG. 6 is an illustration of overbraided thermoplastic members added tothe stackup from FIG. 5 in accordance with an example embodiment.

FIG. 7 is an illustration of stringer bladders added to the stackup fromFIG. 6 in accordance with an example embodiment.

FIG. 8 is an illustration of an overbraided thermoplastic skin added tothe stackup from FIG. 7 in accordance with an example embodiment.

FIG. 9 is an illustration of the second smart susceptor and outertooling positioned around the stackup from FIG. 8 in accordance with anexample embodiment.

FIG. 10 is an illustration of a cross-sectional view of a system forsupporting the consolidation setup during consolidation in accordancewith an example embodiment.

FIG. 11A is an illustration of a portion of the consolidation setup fromFIG. 10 in which the plugs are more clearly seen in accordance with anexample embodiment.

FIG. 11B is an illustration of an enlarged view of one configuration forthe pressurization tube from FIG. 11A in accordance with an exampleembodiment.

FIG. 11C is an illustration of an enlarged view of another configurationfor the pressurization tube from FIG. 11A in accordance with an exampleembodiment.

FIG. 11D is an illustration of an enlarged view of yet anotherconfiguration for the pressurization tube from FIG. 11A in accordancewith an example embodiment.

FIG. 12 is an illustration of a cross-sectional view of the stackuptaken with respect to lines 12-12 in FIG. 11 in accordance with anexample embodiment.

FIG. 13A is an illustration of an isometric view of a tacking-trimmingsetup in accordance with an example embodiment.

FIG. 13B is an illustration of cross-sectional view of thetacking-trimming setup from FIG. 13A in accordance with an exampleembodiment.

FIG. 14 is an illustration of a cross-sectional view of a portion of thetacking-trimming setup in FIG. 13 in accordance with an exampleembodiment.

FIG. 15 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment.

FIG. 16 is a flowchart of a process for building a stackup in accordancewith an example embodiment.

FIG. 17 is a flowchart of a process for building a system that includesa consolidation setup in accordance with an example embodiment.

FIG. 18 is a flowchart of a process for building a system to form acomposite fuselage structure in accordance with an example embodiment.

FIG. 19 is a flowchart of a process for inductively consolidating anoverbraided thermoplastic skin with overbraided thermoplastic members toform a composite fuselage structure in accordance with an exampleembodiment.

FIG. 20 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment.

FIG. 21 is a flowchart of a process for forming a composite fuselagestructure in accordance with an example embodiment.

FIG. 22 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment.

FIG. 23 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment.

FIG. 24 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment.

FIG. 25 is a flowchart of a process for tacking and trimming athermoplastic tow in accordance with an example embodiment.

FIG. 26 is a flowchart of a process for tacking and trimming athermoplastic tow in accordance with an example embodiment.

FIG. 27 is an illustration of an aircraft manufacturing and servicemethod in accordance with an example embodiment.

FIG. 28 is a block diagram of an aircraft in accordance with an exampleembodiment.

DETAILED DESCRIPTION

The example embodiments described below provide methods, apparatuses,and systems for rapidly and efficiently fabricating composite structuressuch as fuselage barrel sections at reduced cost and weight. Inparticular, using thermoplastic materials to fabricate a compositestructure such as a fuselage barrel section may help reduce overallfabrication costs and production times.

The example embodiments described methods, apparatuses, and systems thateliminate the need for autoclaves to cure fuselage barrel structures.The use of autoclaves may be more expensive than desired. Further,autoclaves have thermal mass requirements due to their size andcomplexity that make using autoclaves more time-consuming and lessefficient than desired for fabricating fuselage barrel sections. Byeliminating the need for autoclaves, the example embodiments describedherein reduce the cost and time needed to fabricate fuselage barrelsections. For example, at least some of the example methods forfabricating a fuselage barrel structure described herein may take onetenth of the time that would be required when using an autoclave.

Further, using the systems described herein, less overall heating isrequired because thermoplastic materials are fully reacted and thereforeno curing is required. The systems described herein require less overallequipment and less complex equipment for the fabrication of fuselagebarrel sections as compared to those systems involving autoclaves.

The example embodiments describe creating a composite structure, such asa fuselage barrel section, using overbraided thermoplastic stringersconsolidated to an overbraided thermoplastic skin. Induction heating isused to perform this consolidation in a relatively inexpensive, rapid,and reliable manner. As used herein, “consolidation” or a “consolidationprocess” refers to the process by which components comprised ofoverbraided thermoplastic material are heated to melting such that thecomponents can be joined, fused, or integrated with each other. Thisheating is performed using smart susceptors that allow for fast heatingto a selected temperature and then maintaining that temperatureprecisely. The process may further include cooling the components afterthis joining or integration process to result in a fully integratedstructure.

Once the integrated fuselage barrel structure has been fabricated, otherfuselage components may be easily welded to or otherwise attached to thefuselage barrel structure. For example, without limitation, skin tearstraps, pad-ups, and local reinforcements for a door cutout and servicedoor area may be induction-welded to the fuselage barrel structure viahigh rate production fiber placement and stacking placement ofthermoplastic materials. Fuselage and window frames and other components(e.g., tear straps, intercostals, doublers, shear ties, systemsbrackets, etc.) may also be welded into place using induction weldingtechnology.

Thus, the example embodiments described below provide methods,apparatuses, and systems for forming a composite structure usingthermoplastic materials and induction heating. In one exampleembodiment, a stackup is built in which the stackup a plurality ofoverbraided thermoplastic members and an overbraided thermoplastic skin.The stackup may also include a bladder having a plurality of recessedportions, a plurality cauls within the plurality of recessed portions,and a plurality of stringer bladders. The stackup is placed between aninner tooling and an outer tooling. A load constraint is used to holdthe inner tooling, the stackup, the outer tooling in place. Theconsolidation setup is heated to form the composite structure. Thisheating, which may be performed via induction and using smartsusceptors, co-consolidates the plurality of overbraided thermoplasticmembers with the overbraided thermoplastic skin to thereby form thecomposite structure.

Referring now to the figures, FIG. 1 is a block diagram of amanufacturing environment 100 in accordance with an example embodiment.Within manufacturing environment 100, composite structure 101 is formed.In these illustrative examples, composite structure 101 takes the formof composite fuselage structure 102. Composite fuselage structure 102may be, for example, a composite barrel section. In other illustrativeexamples, composite structure 101 may take some other form.

Composite structure 101 is formed using system 103. System 103 includesconsolidation setup 104, end tooling 105, a plurality of plugs 106, anda plurality of connector devices 107. In these illustrative examples,consolidation setup 104 includes inner tooling 108, outer tooling 110,stackup 112, first smart susceptor 114, second smart susceptor 115,support structure 116, and load constraint 117.

Inner tooling 108 includes a plurality of induction coils 118 embeddedwithin inner tooling 108. In some examples, inner tooling 108 is alsoembedded with a plurality of rods 119. Rods 119 may take the form of,for example, without limitation, fiberglass rods. Rods 119 are used toreinforce inner tooling 108 and to load inner tooling 108 duringcompression.

Similar to inner tooling 108, outer tooling 110 includes a plurality ofinduction coils 120 embedded within outer tooling 110. Inner tooling 108and outer tooling 110 may be comprised of a same material or differenttypes of materials. In one illustrative example, inner tooling 108 andouter tooling 110 are both comprised of a ceramic material.

Stackup 112 is positioned between inner tooling 108 and outer tooling110. In particular, stackup 112 is positioned between first smartsusceptor 114 and second smart susceptor 115, which are located betweeninner tooling 108 and outer tooling 110. For example, first smartsusceptor 114 is positioned between stackup 112 and inner tooling 108.Second smart susceptor 115 is positioned between stackup 112 and outertooling 110.

In these illustrative examples, first smart susceptor 114 and secondsmart susceptor 115 are considered separate from inner tooling 108 andouter tooling 110, respectively. But in other illustrative examples,first smart susceptor 114 may be integrated with or otherwise consideredpart of inner tooling 108, and second smart susceptor 115 may beintegrated with or otherwise considered part of outer tooling 110. Forexample, first smart susceptor 114 and second smart susceptor 115 may beconsidered liners for inner tooling 108 and outer tooling 110,respectively.

Both first smart susceptor 114 and second smart susceptor 115 areelectrically conductive and have high thermal conductivity. Both ofthese smart susceptors absorb electromagnetic energy and convert suchelectromagnetic energy into heat. For example, induction coils 118 andinduction coils 120 may generate an electromagnetic flux field. Firstsmart susceptor 114 and second smart susceptor 115 may be positionedwithin the electromagnetic flux field and includes a magneticallypermeable material that responds to the electromagnetic flux field togenerate heat.

A “smart susceptor,” such as first smart susceptor 114 or second smartsusceptor 115, is typically comprised of a material or materials thatgenerates heat efficiently until reaching a threshold temperature (i.e.,a Curie temperature). As portions of the smart susceptor reach thethreshold temperature, the magnetic permeability of those portionsdecreases. This decrease in magnetic permeability limits the generationof heat by those portions of the smart susceptor and shifts the magneticflux to the lower-temperature portions causing these lower-temperatureportions to more quickly heat up to the threshold temperature.

In this manner, first smart susceptor 114 and second smart susceptor 115are used to help distribute heat and ensure thermal uniformity whenstackup 112 is inductively heated via induction coils 118 and inductioncoils 120. This inductive heating is used to thermally consolidateoverbraided thermoplastic components, described below in FIG. 2, withinstackup 112.

Support structure 116 provides support for consolidation setup 104 andis used to hold inner tooling 108 in place. In some examples, supportstructure 116 is referred to as a mandrel or inner mandrel. Innertooling 108 is positioned around support structure 116.

Load constraint 117 is positioned around outer tooling 110 and helpshold the various components of consolidation setup 104 in place. Inparticular, load constraint 117 helps hold inner tooling 108, firstsmart susceptor 114, stackup 112, second smart susceptor 115, and outertooling 110 in place relative to each other during the formation ofcomposite structure 101.

Consolidation setup 104 has first end 122 and second end 124. Stackup112 within consolidation setup 104 has first end 126 and second end 128.In these illustrative examples, plugs 106 are located at first end 126and second end 128 of stackup 112. End tooling 105 is located at firstend 122 and second end 124 of consolidation setup 104 and used tosupport and secure plugs 106.

Connector devices 107 are used to connect induction coils 118 withinduction coils 120. Connector devices 107 may be located at both firstend 122 and second end 124 of consolidation setup 104. Connector devices107 may take different forms. In one illustrative example, each ofconnector devices 107 takes the form of knife switch connector 127.Knife switch connector 127 may be, for example, a bar of copper or someother highly conductive material that is capable of rotating about afixed pivot point 129.

Consolidation setup 104 is heated inductively using induction coils 118and induction coils 120. In particular, first smart susceptor 114 andsecond smart susceptor 115 are heated inductively via induction coils118 and induction coils 120. These smart susceptors help ensure thermaluniformity in stackup 112, within selected tolerances, duringconsolidation. In the illustrative examples in which composite fuselagestructure 102 is being formed, the result of this consolidation is theintegration of a plurality of fuselage stringers 130 with fuselage skin132.

Fuselage skin 132 may be a circumferential skin in these illustrativeexamples. For example, fuselage skin 132 may be used to form a fullfuselage barrel section. In other illustrative examples, fuselage skin132 may be curved and formed into a half fuselage barrel section, aquarter fuselage barrel section, or some other type of partial fuselagebarrel section.

FIG. 2 is a more detailed illustration of stackup 112 from FIG. 1 inaccordance with an example embodiment. Stackup 112 includes bladder 202,a plurality of cauls 204, a plurality of overbraided thermoplasticmembers 206, a plurality of stringer bladders 208, and overbraidedthermoplastic skin 210. These components of stackup 112 are positionedrelative to each other in a particular manner when used in system 103 toform composite structure 101.

In these illustrative examples, bladder 202 is shaped such that bladder202 has a plurality of recessed portions 212 and a plurality of caps214. Each of recessed portions 212 is located between two of caps 214.Recessed portion 216 is an example of one of recessed portions 212.Recessed portion 216 is located between cap 218 and cap 220 of caps 214.Recessed portion 216 includes main section 222, stepped section 224, andstepped section 226. Stepped section 224 is located at a first edge ofrecessed portion 216 near cap 218. Stepped section 226 is located at asecond edge of recessed portion 216 near cap 220. Main section 222extends between stepped section 224 and stepped section 226. In someexamples, main section 222 includes a base section (that may form the“cap” portion of a hat stringer) and two webbed sections that extendfrom this base section to stepped section 224 and stepped section 226.

Bladder 202 may be comprised of a material that provides a desired levelof elasticity and compliance at high temperatures. In these illustrativeexamples, bladder 202 may be comprised of aluminum (which may be analuminum alloy). The aluminum provides a desired level of elasticity andcompliance at higher temperatures (e.g., temperatures over about 500degrees Fahrenheit). In one illustrative example, bladder 202 iscomprised of an aluminum alloy such as 5083 aluminum alloy, which is analuminum alloyed with magnesium and traces of manganese and chromium. Inother examples, bladder 202 may be referred to as an inner mold line(IML) bladder.

Cauls 204 are positioned within recessed portions 212 of bladder 202.For example, each of cauls 204 may be positioned within a correspondingone of recessed portions 212. Cauls 204 are used to provide a stable,rigid, and smooth surface for overbraided thermoplastic members 206.Each of cauls 204 is comprised of a material selected to provide adesired level of strength to cauls 204 without requiring cauls 204 bethicker than desired. Further, each of cauls 204 is comprised of amaterial selected such that cauls 204 have first coefficient of thermalexpansion 227.

Caul 228 is an example of one of cauls 204. Caul 228 may be positionedwithin recessed portion 216 when used in stackup 112. Caul 228 may bebetween about ⅙th of an inch to about 1/10th of an inch in thickness. Inone illustrative example, caul 228 is about ⅛th of an inch in thickness.Caul 228 may be comprised of a nickel-iron alloy in these illustrativeexamples. In one illustrative example, caul 228 is comprised of an invaralloy comprising between about 40 percent to about 43 percent nickel(e.g., Invar 42). In some illustrative examples, caul 228 may bereferred to as an invar caul.

Caul 228 may be shaped to substantially conform to or match recessedportion 216 of bladder 202. For example, caul 228 may have main section230, flanged section 232, and flanged section 234. Main section 230substantially matches main section 222 of recessed portion 216. Thus, insome cases, main section 230 includes a base section and two webbedsections extending from the base section to flanged section 232 andflanged section 234. Flanged section 232 is shaped to fit within or sitover stepped section 224. Similarly, flanged section 234 is shaped tofit within or sit over stepped section 226.

Overbraided thermoplastic members 206 are positioned over cauls 204. Inparticular, each of overbraided thermoplastic members 206 is positionedrelative to a corresponding one of cauls 204. Overbraided thermoplasticmembers 206 are shaped similarly to cauls 204. In these illustrativeexamples, cauls 204 and overbraided thermoplastic members 206 havethicknesses that ensure overbraided thermoplastic members 206 do notextend past the profile (e.g., circumferential profile) of bladder 202defined by caps 214 of bladder 202.

Overbraided thermoplastic members 206 may be formed using availableapparatuses and techniques for overbraiding continuous fibers ofthermoplastic composite materials. Overbraiding enables a large numberof spools of continuous fiber thermoplastic materials to be used atonce. For example, with overbraiding, the spools may number in thehundreds, thereby enabling high rates of material application.

Overbraided thermoplastic members 206 have second coefficient of thermalexpansion 235. In these illustrative examples, first coefficient ofthermal expansion 227 of cauls 204 is within a desired range of secondcoefficient of thermal expansion 235 of overbraided thermoplasticmembers 206.

For example, cauls 204 may be made from a material such that firstcoefficient of thermal expansion 227 of cauls 204 is closer to secondcoefficient of thermal expansion 235 of overbraided thermoplasticmembers 206 as compared to third coefficient of thermal expansion 237 ofbladder 202. In some cases, the material of cauls 204 may be selectedsuch that first coefficient of thermal expansion 227 of cauls 204 is asclose as possible to second coefficient of thermal expansion 235 ofoverbraided thermoplastic members 206.

With cauls 204 and overbraided thermoplastic members 206 havingcoefficients of thermal expansion that are close, cauls 204 are capableof maintaining a desired strength and rigidity during induction heatingto help overbraided thermoplastic members 206 retain their smoothnessand shape during induction heating. For example, the aluminum that makesup bladder 202 may have third coefficient of thermal expansion 237 thatis not close to second coefficient of thermal expansion 235 ofoverbraided thermoplastic members 206. For example, third coefficient ofthermal expansion 237 may be much lower than second coefficient ofthermal expansion 235. Therefore, during induction heating, bladder 202may soften. Without cauls 204, the softening of bladder 202 might causeundesired undulations in overbraided thermoplastic members 206. Thus,cauls 204 provide a well-defined surface for overbraided thermoplasticmembers 206 while reducing or eliminating the potential issuesassociated with the differences in coefficients of thermal expansionbetween bladder 202 and overbraided thermoplastic members 206.

Stringer bladders 208 are positioned over overbraided thermoplasticmembers 206. Stringer bladders 208 are shaped to nest within theremaining space within recessed portions 212 of bladder 202 withoutextending beyond the profile (e.g., circumferential profile) of bladder202.

In these illustrative examples, stringer bladders 208 may be comprisedof an aluminum (which may be an aluminum alloy). The aluminum mayprovide a desired level of elasticity and compliance at highertemperatures (e.g., temperatures over about 500 degrees Fahrenheit). Forexample, during induction heating, the aluminum may become compliant andsoft such that stringer bladders 208 provide substantially even pressureover overbraided thermoplastic members 206. In other words, stringerbladders 208 comprised of aluminum help provide even pneumatic pressureto help ensure that a pressure gradient is not created. In oneillustrative example, stringer bladders 208 are comprised of an aluminumalloy such as 5083 aluminum alloy, which is an aluminum alloyed withmagnesium and traces of manganese and chromium.

Overbraided thermoplastic skin 210 is positioned over stringer bladders208 in a manner such that overbraided thermoplastic skin 210 alsocontacts portions 236 of overbraided thermoplastic members 206 and caps214 of bladder 202. During induction heating, overbraided thermoplasticskin 210 is consolidated with overbraided thermoplastic members 206.

In particular, overbraided thermoplastic skin 210 and overbraidedthermoplastic members 206 are co-consolidated. Induction heating is usedto heat overbraided thermoplastic skin 210 and overbraided thermoplasticmembers 206 to melting such that overbraided thermoplastic skin 210 andoverbraided thermoplastic members 206 are integrated or joined together.In this manner, after consolidation and cooling, overbraidedthermoplastic skin 210 and overbraided thermoplastic members 206together form a single, integrated structure, composite structure 101 inFIG. 1. In some cases, one or more additional consolidation processesmay be performed to integrate or join other structural features tocomposite structure 101.

More specifically, overbraided thermoplastic skin 210 is consolidatedwith portions 236 of overbraided thermoplastic members 206 to form anintegrated composite structure 101. When composite structure 101 takesthe form of composite fuselage structure 102, overbraided thermoplasticskin 210 form fuselage skin 132 and overbraided thermoplastic members206 form fuselage stringers 130.

In these illustrative examples, a plurality of pressurization tubes 238may be inserted within or passed through stringer bladders 208.Pressurization tubes 238 may at least partially extend into stringerbladders 208. Pressurization tubes 238 help apply pressure withinstringer bladders 208. For example, a pressurization system (not shown)may connect to pressurization tubes 238 through tubing to allow an inertgas to flow through pressurization tubes 238.

In some examples, each of pressurization tubes extends into but does notfully extend through a corresponding one of stringer bladders 208. Forexample, pressurization tubes 238 may open into corresponding ones ofstringer bladders 208. This allows the inert gas flowing throughpressurization tubes 238 to exit out of pressurization tubes 238 intostringer bladders 208 to thereby pressurize stringer bladders 208. Inother examples, each of pressurization tubes 238 may extend through theentire length of the corresponding one of stringer bladders 208. But inthese cases, pressurization tubes 238 have openings (e.g., perforations,slits, holes or some other type of openings) that allow the inert gas toenter stringer bladders 208. The pressurization system controls the flowof the inert gas and uses the inert gas to control the pressure withinstringer bladders 208.

In one illustrative example, pressurization tubes 238 are comprised ofaluminum. In other examples, pressurization tubes 238 may be comprisedof stainless steel, some other type of material, or a combinationthereof. The pressurization system may use the inert gas to increase thepressure within pressurization tubes 238, and thereby stringer bladders208. During induction heating, this pressurization helps stringerbladders 208 expand to provide support to overbraided thermoplasticmembers 206 to prevent overbraided thermoplastic from caving in (orcollapsing inward) or otherwise moving out of a desired shape.Additionally, this pressurization helps stringer bladders 208 expand toprovide a smooth surface for overbraided thermoplastic members 206 andoverbraided thermoplastic skin 210.

Further, the pressure within bladder 202 may also be controlled usingpressurization tube 240 that extends into bladder 202 and thepressurization system described above. For example, pressurization tube240 may also be comprised of aluminum. In other examples, pressurizationtube 240 may be comprise of stainless steel, some other material, or acombination thereof. The pressurization system may use the inert gas tocontrol the pressure within pressurization tube 240, and thereby bladder202, similar to pressurization tubes 238.

In one illustrative example, pressurization tube 240 enters into bladder202 without extending all the way through bladder 202. In this manner,inert gas may flow out of pressurization tube 240 and into bladder 202to thereby pressurize bladder 202. In other examples, pressurizationtube 240 has openings (e.g., perforations, slits, holes, or some othertype of opening) that allows gas to flow from pressurization tube 240into bladder 202.

Each of stringer bladders 208 is pressurized to a substantially samepressure (i.e., a same pressure within selected tolerances) duringconsolidation. This helps ensure that the expansion of each of stringerbladders 208 is even such that the same force is applied to each ofoverbraided thermoplastic members 206 during consolidation. In somecases, bladder 202 and stringer bladders 208 are pressurized to asubstantially same pressure during consolidation of overbraidedthermoplastic members 206 to overbraided thermoplastic skin 210.Increasing the pressure within bladder 202 and stringer bladders 208causes some expansion, which places the preform (i.e., overbraidedthermoplastic members 206 and overbraided thermoplastic skin 210) intension during processing. Further, this expansion helps co-consolidatestackup 112 during processing by pushing against or compressing stackup112 against outer tooling 110.

System 103 of FIG. 1 with stackup 112 of FIGS. 1 and 2 allowsconsolidation of overbraided thermoplastic members 206 with overbraidedthermoplastic skin 210 to form composite structure 101 in an efficientmanner at rapid rates. In particular, using induction heating viainduction coils 118, induction coils 120, first smart susceptor 114, andsecond smart susceptor 115 helps ensure a rapid and reliableconsolidation process.

The illustrations of manufacturing environment 100 and system 103 inFIG. 1 and stackup 112 in FIGS. 1 and 2 are not meant to imply physicalor architectural limitations to the manner in which an illustrativeembodiment may be implemented. Other components in addition to or inplace of the ones illustrated may be used. Some components may beoptional. Also, the blocks are presented to illustrate some functionalcomponents. One or more of these blocks may be combined, divided, orcombined and divided into different blocks when implemented in anillustrative embodiment.

FIGS. 3A and 3B are illustrations of a consolidation setup in accordancewith an example embodiment. FIG. 3A is an illustration of an isometriccross-sectional view of the consolidation setup. Consolidation setup 300is an example of one implementation for consolidation setup 104 in FIG.1.

Consolidation setup 300 includes support structure 302, inner tooling304, stackup 306, outer tooling 308, and load constraint 310.Consolidation setup 300 further includes first smart susceptor 311 andsecond smart susceptor 312. First smart susceptor 311 is positionedbetween inner tooling 304 and stackup 306 and second smart susceptor 312is positioned between stackup 306 and outer tooling 308.

Support structure 302, inner tooling 304, stackup 306, outer tooling308, and load constraint 310 are examples of implementations for supportstructure 116, inner tooling 108, stackup 112, outer tooling 110, andload constraint 117, respectively, in FIG. 1. First smart susceptor 311and second smart susceptor 312 are examples of implementations for firstsmart susceptor 114 and second smart susceptor 115, respectively, inFIG. 1. Support structure 302, inner tooling 304, stackup 306, outertooling 308, load constraint 310, first smart susceptor 311, and secondsmart susceptor 312 are aligned with respect to longitudinal axis 301(e.g., center longitudinal axis). In one illustrative example, thesecomponents are concentrically aligned with respect to longitudinal axis301.

FIG. 3B is an illustration of a cross-sectional view of theconsolidation setup from FIG. 3A. The cross-sectional view ofconsolidation setup 300 in FIG. 3B is taken along a plane perpendicularto longitudinal axis 301 through consolidation setup 104. In particular,the cross-sectional view of consolidation setup 300 in FIG. 3B is takenwith respect to lines 3B-3B in FIG. 3A.

In these illustrative examples, support structure 302 provides supportto inner tooling 304 and is separate from inner tooling 304. In otherillustrative examples, support structure 302 may be considered part ofinner tooling 304 or integrated with inner tooling 304. Inner tooling304 has induction coils 313 embedded within inner tooling 304. Inductioncoils 313 are an example of one implementation for induction coils 118in FIG. 1. Outer tooling 308 has induction coils 314 embedded withinouter tooling 308. Induction coils 314 are an example of oneimplementation for induction coils 118 in FIG. 1.

In one or more illustrative examples, inner tooling 304, stackup 306,outer tooling 308, and load constraint 310 are substantially cylindricalstructures. For example, inner tooling 304, stackup 306, outer tooling308, and load constraint 310 may be concentrically aligned with respectto longitudinal axis 301. In one illustrative example, inner tooling 304is formed from a single cylindrical structure. In other illustrativeexamples, inner tooling 304 is formed from two halves that may be puttogether to form a cylindrical structure.

Both inner tooling 304 and outer tooling 308 may be comprised of aceramic material. Ceramic material is a dielectric material that is“transparent” to and does not react with the magnetic energy produced byinduction coils 313 and induction coils 314. In this manner, themagnetic energy can pass through the ceramic material to interact withfirst smart susceptor 311 and second smart susceptor 312. First smartsusceptor 311 and second smart susceptor 312 convert the magnetic energyto thermal energy, but the ceramic material is considered “opaque” tothe thermal energy so that the thermal energy does not pass through theceramic material. In this manner, the ceramic material helps prevent theloss of thermal energy during induction heating by working as a thermalinsulator. Further, ceramic material has a low coefficient of thermalexpansion that helps inner tooling 304 and outer tooling 308 withstandthe thermal gradients associated with the other components ofconsolidation setup 300 during induction heating.

In these illustrative examples, inner tooling 304 includes rods 316embedded within this ceramic material. Rods 316 are positionedsubstantially parallel to longitudinal axis 301. Further, rods 316 maybe positioned circumferentially around longitudinal axis 301. As seen inFIG. 3, rods 316 are positioned closer to longitudinal axis 301 thaninduction coils 313. Rods 316 are an example of one implementation forrods 119 in FIG. 2. Rods 316 are fiberglass rods in these examples. Rods316 being comprised of fiberglass, which is a dielectric material, helpsrods 316 to provide compressive loading within inner tooling 304. Rods316 help put the ceramic material of inner tooling 304 in compression asthe various components of consolidation setup 300 are added onto innertooling 304, which helps with the long-term durability of inner tooling304. In this manner, rods 316 reinforce inner tooling 304 and load innertooling 108 during compression.

Stackup 306 is built up around inner tooling 304. Outer tooling 308 ispositioned around stackup 306. In particular, outer tooling 308 ispositioned around second smart susceptor 312, which is positioned aroundstackup 306. Similar to inner tooling 304, outer tooling 308 may becomprised of a ceramic material.

In these illustrative examples, outer tooling 308 is comprised of twohalves that are brought together around stackup 306. For example, afastener system (not shown) may be used to connect the two halves ofouter tooling 308. In some cases, load constraint 310 is used to holdthe two halves of outer tooling 308 in place. Similarly, load constraint310 may be comprised of two halves that are brought together aroundouter tooling 308 to secure outer tooling 308, stackup 306, and innertooling 304 together. A fastener system (not shown) may be used toconnect these two halves of load constraint 310. In some cases, the samefastener system may be used to connect the two halves of both outertooling 308 and load constraint 310. The fastener system may include,for example, a clamping system (e.g., hydraulic clamps) that allows foreasy clamping and easy release. In other illustrative examples, outertooling 308, load constraint 310, or both may be a single cylindricalstructure.

FIGS. 4-8 illustrate the buildup of stackup 306 from FIG. 3 over innertooling 304 in accordance with an example embodiment. FIG. 4 is anillustration of a portion of inner tooling 304 from FIG. 3 taken betweenlines 4-4 in FIG. 3 in accordance with an example embodiment. Firstsmart susceptor 311 is positioned around inner tooling 304 such thatfirst smart susceptor 311 is positioned within the electromagnetic fluxfield generated by induction coils 118 when a current is run throughinduction coils 118.

Bladder 400 is positioned over and around first smart susceptor 311.Bladder 400 is an example of one implementation for bladder 202 in FIG.2. Bladder 400 is the first component added to form stackup 306 fromFIG. 3. Bladder 400 is an aluminum bladder in this illustrative example.During the induction consolidation process, bladder 400 is pressurized.Without pressurization, bladder 400 may be considered “deflated.” Whenpressure is applied to bladder 400, bladder 400 may be considered“inflated.” Pressure may be applied to bladder 400 via an inert gas thatflows through a pressurization tube (not shown in this view) extendingthrough bladder 400 or a channel that extends through bladder 400.

Bladder 400 includes recessed portions 402 formed between caps 404.Recessed portions 402 are used to help index the locations for thefuselage stringers being formed. Recessed portion 406 is an example ofone of recessed portions 402. Recessed portion 406 is formed between cap408 and cap 410 of caps 404.

Recessed portion 406 is shaped such that recessed portion 406 includesmain section 412, stepped section 414, and stepped section 415. Steppedsection 414 is located between main section 412 and cap 408 and steppedsection 415 is located between main section 412 and cap 410. Steppedsection 414 has depth 416 and stepped section 415 has depth 418. Depth416 is measured as the distance between cap 408 and main section 412 anddepth 418 is measured as the distance between cap 410 and main section412. Depth 416 and depth 418 are substantially equal in thisillustrative example.

In this illustrative example, recessed portion 406 (i.e., main section412, stepped section 414, and stepped section 415) is shaped to receivea caul that is shaped to form a “hat” stringer. For example, mainsection 412 may include base section 420 (forming the “cap” portion ofthe hat stringer) and web section 422 and web section 424 that extendfrom base section 420 to stepped section 414 and stepped section 415,respectively. In other illustrative examples, recessed portion 406 maybe shaped to receive some other type of caul.

FIG. 5 is an illustration of cauls added to stackup 306 from FIG. 4 inaccordance with an example embodiment. Cauls 500 are positioned withinrecessed portions 402 of bladder 400. Cauls 500 are an example of oneimplementation for cauls 204 in FIG. 2. In particular, each of cauls 500is positioned within a corresponding one of recessed portions 402.

Further, each of cauls 500 is shaped such that the caul substantiallyconforms to or matches the shape of the corresponding recessed portionwithin which it is placed. In these illustrative examples, cauls 500 areshaped to enable the formation of “hat” stringers.

As previously described, cauls 500 may have a coefficient of thermalexpansion that is sufficiently close to the coefficient of thermalexpansion of overbraided thermoplastic members that will be laterpositioned over cauls 500 to thereby reduce or prevent undue stress frombeing introduced to the thermoplastic material. Cauls 500 are used toprovide strength and rigidity during induction heating because bladder400 softens during induction heating.

For example, caul 502 of cauls 500 is positioned within recessed portion406. Caul 502 is an example of one implementation for caul 228 in FIG.2. Caul 502 is shaped to substantially conform to or match the shape ofrecessed portion 406. Specifically, caul 502 is shaped to substantiallymatch the shape of main section 412, stepped section 414, and steppedsection 415 of recessed portion 406.

For example, caul 502 includes main section 504, flanged section 506,and flanged section 508. Main section 504 is shaped to fit securelywithin main section 412 of recessed portion 406. As previouslydescribed, main section 412 forms at least a portion of across-sectional hat shape. Thus, similar to main section 412, mainsection 504 similarly includes base section 510, web section 512, andweb section 514. Flanged section 506 and Flanged section 508 are shapedto sit securely within stepped section 414 and stepped section 415,respectively, of recessed portion 406. In this illustrative example,flanged section 506 has a thickness less than depth 416 of steppedsection 414. Flanged section 508 has a thickness less than depth 418 ofstepped section 415.

FIG. 6 is an illustration of overbraided thermoplastic members added tostackup 306 from FIG. 5 in accordance with an example embodiment.Overbraided thermoplastic members 600 are positioned over cauls 500.Overbraided thermoplastic members 600 are examples of implementationsfor overbraided thermoplastic members 206 in FIG. 2. Each of overbraidedthermoplastic members 600 is positioned over a corresponding one ofcauls 500.

In some illustrative examples, overbraided thermoplastic members 600 arelaid up directly over cauls 500 after cauls 500 have been added tostackup 306. In other illustrative examples, overbraided thermoplasticmembers 600 may be added to stackup 306 at the same time as cauls 500.For example, overbraided thermoplastic members 600 may be laid up overcauls 500 prior to being added to stackup 306. Cauls 500 may then beused to transport and locate overbraided thermoplastic members 600 inthe various recessed portions of bladder 400.

Further, each of overbraided thermoplastic members 600 is substantiallyconformed to the shape of the corresponding caul. Overbraidedthermoplastic members 600 will ultimately form “hat” stringers.

As one example, overbraided thermoplastic member 602 is positioned overcaul 502, which is positioned within recessed portion 406 of bladder400. Overbraided thermoplastic member 602 is substantially conformed tothe shape of caul 502. Specifically, overbraided thermoplastic member602 is substantially conformed to the shape of main section 504, flangedsection 506, and flanged section 508 of caul 502. This shaping ofoverbraided thermoplastic member 602 results in overbraidedthermoplastic member 602 having main section 604, flanged section 606and flanged section 608.

In this illustrative example, flanged section 606 of overbraidedthermoplastic member 602 and flanged section 506 of caul 502 have acombined thickness that is substantially equal to depth 416 of steppedsection 414 of recessed portion 406 of bladder 400. Similarly, flangedsection 608 of overbraided thermoplastic member 602 and flanged section508 of caul 502 have a combined thickness that is substantially equal todepth 418 of stepped section 415 of recessed portion 406 of bladder 400.In this manner, overbraided thermoplastic member 602 does not extendpast the circumferential profile of cap 408 or cap 410.

FIG. 7 is an illustration of stringer bladders added to stackup 306 fromFIG. 6 in accordance with an example embodiment. Stringer bladders 700are positioned over overbraided thermoplastic members 600. Stringerbladders 700 are an example of one implementation for stringer bladders208 in FIG. 1. Each of stringer bladders 700 is shaped to ensure thatoverbraided thermoplastic members 600 retain their desired shape for theformation of “hat” stringers.

Each of stringer bladders 700 is positioned over a corresponding one ofoverbraided thermoplastic members 600. For example, stringer bladder 702is positioned over overbraided thermoplastic member 602.

In this illustrative example, stringer bladder 702 is shaped to ensurethat overbraided thermoplastic member 602 maintains its shape duringheating. Together, recessed portion 406 of bladder 400, caul 502, andstringer bladder 702 support both sides of overbraided thermoplasticmember 602, while securing overbraided thermoplastic member 602 inplace. Stringer bladder 702 is shaped and sized such that side 704 ofstringer bladder 702 follows the general circumferential outline formedby caps 404 of bladder 400.

Similar to bladder 400, stringer bladders 700 are pressurized during theinduction consolidation process. Without pressurization, stringerbladders 700 may be considered “deflated.” Once pressurized, stringerbladders 700 may be considered “inflated.”

FIG. 8 is an illustration of an overbraided thermoplastic skin added tostackup 306 from FIG. 7 in accordance with an example embodiment.Overbraided thermoplastic skin 800 is positioned over caps 404 ofbladder 400, stringer bladders 700, and selected portions of overbraidedthermoplastic members 600. In particular, overbraided thermoplastic skin800 is positioned such that overbraided thermoplastic skin 800 contactsthe flanged sections of overbraided thermoplastic members 600. Forexample, overbraided thermoplastic skin 800 contacts flanged section 606and flanged section 608 of overbraided thermoplastic member 602.

In this illustrative example, overbraided thermoplastic skin 800surrounds the entire circumference of the portion of stackup 306 formedby bladder 400, cauls 500, overbraided thermoplastic members 600, andstringer bladders 700. The addition of overbraided thermoplastic skin800 completes the formation of stackup 306 in these illustrativeexamples.

FIG. 9 is an illustration of second smart susceptor 312 and outertooling 308 positioned around stackup 306 from FIG. 8 in accordance withan example embodiment. Second smart susceptor 312 is positioned aroundoverbraided thermoplastic skin 800. Outer tooling 308 is positionedaround second smart susceptor 312. This placement ensures that secondsmart susceptor 312 is positioned within the electromagnetic flux fieldgenerated by induction coils 314 when a current is run through inductioncoils 314.

Through induction coils 313 and induction coils 314, first smartsusceptor 311 and second smart susceptor 312 are used to heat and causeconsolidation of overbraided thermoplastic skin 800 and overbraidedthermoplastic members 600. This consolidation results in a finalfuselage structure comprised of a fuselage skin with integrated fuselagestringers.

FIG. 10 is an illustration of a longitudinal cross-sectional view of asystem for supporting consolidation setup 300 during consolidation inaccordance with an example embodiment. This cross-sectional view ofsystem 1000, and thereby consolidation setup 300, is taken alone a planesubstantially parallel to longitudinal axis 301. In particular, thiscross-sectional view is taken with respect to lines 10-10 in FIG. 3A andincludes additional components that were not shown in FIG. 3A. System1000 is an example of one implementation for system 113 in FIG. 1.

As depicted in FIG. 10, stackup 306 has first end 1002 and second end1004. System 1000 includes a plurality of plugs 1005 for use in pluggingthese ends. In particular, plug 1006 and plug 1008 are used to plugfirst end 1002 and second end 1004, respectively, of stackup 306.

Plugs 1005 help ensure that the various components of stackup 306 remainin place during induction heating. For example, plugs 1005 do not expandlongitudinally to the extent that bladder 400 and stringer bladders 700may expand to thereby reduce undesired longitudinal expansion of bladder400 and stringer bladders 700. For example, plugs 1005 may not expand atall or may expand only slightly as compared to bladder 400 and stringerbladders 700. The sizing of plugs 1005 may be selected to help ensurethat the various components of stackup 306 remain in place duringinduction heating.

Further, plugs 1005 provide an easy and efficient way of loading andunloading components in system 1000. Plugs 1005 may be removed to allowthe various components of stackup 306 to be unloaded longitudinally. Forexample, bladder 400 and stringer bladders 700 may be slid out of system1000 in a longitudinal direction when plugs 1005 are removed.

System 1000 further includes end tooling 1010 that is used to locate andsecure plug 1006 and plug 1008. End tooling 1010 may be, for example, astructural frame or system that helps secure plug 1006 and plug 1008 inplace relative to stackup 306.

Connector devices 1012 are used to connect induction coils 313 toinduction coils 314. In one illustrative example, each of connectordevices 1012 is used to connect one of induction coils 313 embeddedwithin inner tooling 304 to a corresponding one of induction coils 314embedded within outer tooling 308 at a particular end of consolidationsetup 300. In some illustrative examples, each of connector devices 1012is a knife switch connection. For example, each of connector devices1012 may include a bar of copper or some other highly conductivematerial that is capable of rotating about a fixed pivot point.

In this example, connector devices 1012 include connector device 1014,connector device 1016, connector device 1018, and connector device 1020.Connector device 1014 connects coil 1022 of induction coils 313 withcoil 1024 of induction coils 314 at end 1026 of consolidation setup 300.Connector device 1016 connects coil 1022 with coil 1024 at end 1028 ofconsolidation setup 300. Connector device 1018 connects coil 1030 ofinduction coils 313 with coil 1032 of induction coils 314 at end 1026 ofconsolidation setup 300. Connector device 1020 connects coil 1030 withcoil 1032 at end 1028 of consolidation setup 300.

In some illustrative examples, consolidation setup 300 further includespressure bladders 1038. Each of pressure bladders 1038 is used to applypressure at a corresponding one of plugs 1005. Pressure bladder 1040 isan example of one of pressure bladders 1038. Pressure bladder 1040 isused to apply pressure to in a manner that improves the electricalcontact between first smart susceptor 311 and second smart susceptor 312(not labeled in this view) and connector device 1014. Pressure bladder1040 may take the form of a stainless-steel bladder.

FIG. 11A is an illustration of a portion of consolidation setup 300 fromFIG. 10 in which plug 1006 and plug 1008 are more clearly seen inaccordance with an example embodiment. In this view, caul 502 isvisible. Stringer bladder 702 located within the recessed portion ofcaul 502 is also present but not shown in this view. Further, thiscross-sectional view is taken so that

Plug 1006 and plug 1008 are used to plug first end 1002 and second end1004 of stackup 306. Plug 1006 and plug 1008 are implemented similarly.In these examples, plug 1006 includes plug portion 1100, thermalinsulation layer 1102, and susceptor connector 1104. Plug 1008 similarlyincludes plug portion 1106, thermal insulation layer 1108, and susceptorconnector 1110.

Thermal insulation layer 1102 and thermal insulation layer 1108 providea way of insulating susceptor connector 1104 and susceptor connector1110, respectively. These thermal insulation layers may be comprised of,for example, a dielectric material. In these examples, susceptorconnector 1104 and susceptor connector 1110 are water-cooled susceptorconnectors. If susceptor connector 1104 and susceptor connector 1110were to get too hot, undesired heating, oxide buildup, or both mightoccur. Thus, susceptor connector 1104 and susceptor connector 1110 arewater-cooled to prevent overheating.

Pressurization tube 1112 is an example of one implementation for one ofpressurization tubes 238 in FIG. 2. In these illustrative examples,pressurization tube 1112 extends through stringer bladder 702 of stackup306 (not shown in this view), past both ends of stringer bladder 702,and out from both first end 1002 and second end 1004 of stackup 306. Asdepicted, pressurization tube 1112 includes end 1114 and end 1116. Inthese examples, end 1114 and end 1116 of pressurization tube 1112extends into plug portion 1100 and plug portion 1106, respectively, butdo not extend past these plug portions. In other words, the ends ofpressurization tube 1112 do not extend into thermal insulation layer1102 or thermal insulation layer 1108. In some cases, however, the endsof pressurization tube 1112 may extend all the way through and past plug1006 and plug 1008.

A pressurization system (not shown) may be used to cause an inert gas toflow through pressurization tube 1112 and into stringer bladder 702 (notshown in this view). For example, both end 1114 and end 1116 may be openand connected to tubing that is connected to the pressurization systemto allow the inert gas to flow into pressurization tube 1112.Pressurization tube 1112 may be implemented in various ways.

FIG. 11B is an illustration of an enlarged view of one configuration forpressurization tube 1112 from FIG. 11A in accordance with an exampleembodiment. In FIG. 11B, caul 502 from FIG. 11 is not shown such thatstringer bladder 702 nested within caul 502 may be more clearly seen. Inthis illustrative example, pressurization tube 1112 is a discontinuouspressurization tube that enters stringer bladder 702 without extendingall the way through stringer bladder 702.

In particular, pressurization tube 1112 includes opening 1118 andopening 1120 that open into stringer bladder 702. In this manner, theinert gas flowing within pressurization tube 1112 may flow out ofpressurization tube 1112 and directly into stringer bladder 702 viaopening 1118 and opening 1120 to thereby pressurize stringer bladder702. Opening 1118 and opening 1120 may be sized according topressurization requirements.

FIG. 11C is an illustration of an enlarged view of another configurationfor pressurization tube 1112 from FIG. 11A in accordance with an exampleembodiment. In FIG. 11C, caul 502 from FIG. 11 is not shown such thatstringer bladder 702 nested within caul 502 may be more clearly seen. Inthis illustrative example, pressurization tube 1112 is a continuous tubethat extends all the way through stringer bladder 702. In this example,pressurization tube 1112 has one or more openings 1122 that enable theinert gas to flow out of pressurization tube 1112 and into stringerbladder 702 to thereby pressurize stringer bladder 702. Openings 1122may take different forms. For example, openings 1122 may be slits,perforations, holes, or some other type of opening in pressurizationtube 1112.

FIG. 11D is an illustration of an enlarged view of yet anotherconfiguration for pressurization tube 1112 from FIG. 11A in accordancewith an example embodiment. In FIG. 11D, caul 502 from FIG. 11 is notshown such that stringer bladder 702 nested within caul 502 may be moreclearly seen. In this illustrative example, pressurization tube 1112 isa multitube pressurization tube.

In particular, pressurization tube 1112 includes first tube 1123 andsecond tube 1124. First tube 1123 is a discontinuous tube that entersstringer bladder 702 and having end 1126 and end 1128 that terminatewithin stringer bladder 702. Second tube 1124 is a continuous tubelocated within first tube 1123 that extends from end 1114 to end 1116.For example, second tube 1124 has a smaller diameter than first tube1123 and may be comprised of a harder material than pressurization tube1112 to provide structural support to second tube 1124. In one example,first tube 1123 is comprised of aluminum and second tube 1124 iscomprised of stainless steel. Second tube 1124 has one or more openings1130 (e.g., perforations, slits, holes, etc.) that allow an inert gasflowing through second tube 1124 to enter stringer bladder 702.

The inert gas flows into stringer bladder 702 to pressurize stringerbladder 702 and thereby ensure expansion of stringer bladder 702. Thisexpansion helps ensure compression against provide a smooth,well-defined surface for overbraided thermoplastic member 602 shown inFIGS. 7-9.

FIG. 12 is an illustration of a cross-sectional view of stackup 306taken with respect to lines 12-12 in FIG. 11 in accordance with anexample embodiment. In this illustrative example, stringer bladder 702is not shown so, thereby making plug portion 1100 visible.

Channel 1200 extends through stringer bladder 702 and through plugportion 1100 of plug 1008. Channel 1200 is used to receivepressurization tube 1112 from FIG. 11. Channel 1202 extends through plug1006 and through bladder 400 (not shown in this view). Channel 1202 isused to receive a pressure bladder or pressurization tube that is usedto apply pressure to bladder 400 during the induction consolidationprocess. Channel 1202 may be located anywhere that facilitates gasdelivery to bladder 400.

FIGS. 13A and 13B are illustrations of a tacking-trimming setup inaccordance with an example embodiment. FIG. 13A is an illustration of anisometric view of tacking-trimming setup 1300. The tacking-trimmingsetup 1300 may also be referred to as a tow tacking and trimmingapparatus. FIG. 13B is an illustration of a cross-sectional view oftacking-trimming setup 1300. This cross-sectional view oftacking-trimming setup 1300 is taken with respect to lines 13B-13B inFIG. 13A. The description below is in reference to both FIGS. 13A and13B.

Tacking-trimming setup 1300 may be used to create the “tacking” and“trimming” needed for each braided ply of an overbraided thermoplasticcomponent, such as one of overbraided thermoplastic members 600 oroverbraided thermoplastic skin 800 in FIGS. 6-10.

In this illustrative example, tacking-trimming setup 1300 includestacking-trimming system 1301. Tacking-trimming system 1301 is secured tosupport system 1302 which surrounds surface 1304. In these illustrativeexamples, tacking-trimming system 1301 may be secured to support system1302 using a fastener system, a clamping system, a mounting structure,some other type of attachment device, or a combination thereof. Braidedlayup 1306, which may be an example of one type of braided structure, ispositioned around surface 1304. Braided layup 1306 may be a layup ofplies of overbraided continuous thermoplastic composite fibers.Conductive component 1308 is positioned around braided layup 1306.

Although only One tacking-trimming system 1301 is shown secured tosupport system 1302, any number of tacking-trimming systems may bedistributed along support system 1302. In these illustrative examples,support system 1302 includes support ring 1303. Support ring 1303 issized and shaped to fully surround surface 1304.

Support system 1302 travels with a braiding ring or braider (not shownin this view) to enable the adding and dropping of plies in a directionalong longitudinal axis 1307 to create and add to braided layup 1306. Inother words, plies may be added and dropped longitudinally. Further,support system 1302 may rotate about longitudinal axis 1307 ortacking-trimming system 1301 may move around support system 1302 toenable the adding and dropping of plies around surface 1304circumferentially. Conductive component 1308, which may also be referredto as a “shoe,” also travels with the braiding ring or braider.

In one illustrative example, surface 1304 may be the surface formed bybladder 400, stringer bladders 700, and overbraided thermoplasticmembers 600 in FIG. 7 before overbraided thermoplastic skin 800 fromFIG. 8 is added. In this example, overbraided thermoplastic skin 800 islaid up over surface 1304 as braided layup 1306. Tacking-trimming system1301 may be used to tack weld and trim during or after the layup ofoverbraided thermoplastic skin 800.

In other illustrative examples, surface 1304 may be the surface formedby cauls 500. In these examples, overbraided thermoplastic members 600from FIG. 6 are laid up over surface 1304 to form braided layup 1306.Tacking-trimming system 1301 may be used to tack weld and trim during orafter the layup of overbraided thermoplastic members 600 but prior tothe consolidation of overbraided thermoplastic members 600 withoverbraided thermoplastic skin 800. In some cases, when overbraidedthermoplastic members 600 in FIG. 6 are transported to stackup 306 viacauls 500, tacking-trimming system 1301 may be used to tack weld andtrim the already formed layup of overbraided thermoplastic members 600.For example, support system 1302 may be sized and shaped to operativelyplace tacking-trimming system 1301 relative to stackup 306, which mayalso be referred to as a cylindrical thermoplastic stackup.

Tack welding may be performed longitudinally, circumferentially, orboth. Further, tack welding may be used to add and drop plies in amanner that allows complicated preform structures to be formed. Forexample, braided layup 1306 may include a plurality of plies that arenot all continuous layers. Some plies may be partial layers. In somecases, braided layup 1306 includes padups and pad downs. Thus, braidedlayup 1306 may have varying thicknesses and contours along braided layup1306. Tack welding is used to help maintain the structural integrity ofbraided layup 1306.

In still other illustrative examples, tacking-trimming system 1301 maybe used to add local features to braided layup 1306. For example, whenbraided layup 1306 takes the form of overbraided thermoplastic skin 800in FIG. 8, tacking-trimming system 1301 may be used to tack weld andtrim localized features (e.g., padups) that are added to overbraidedthermoplastic skin 800.

In this manner, tacking-trimming system 1301 may be used to provide andmaintain a desired architecture for braided layup 1306. In theseillustrative examples, tacking-trimming system 1301 is used for tackwelding and trimming prior to consolidation. But in other illustrativeexamples, tacking-trimming system 1301 may be used to tack weld and trimlocalized layup features that are added to an integrated structure(e.g., fuselage barrel section) that has already gone through at leastone consolidation process.

FIG. 14 is an illustration of a cross-sectional view of a portion oftacking-trimming setup 1300 in FIG. 13 in accordance with an exampleembodiment. This view of tacking-trimming setup 1300 is taken withrespect to lines 14-14 in FIG. 13.

As depicted, tacking-trimming system 1301 is secured to support system1302. Tacking-trimming system 1301 includes tack welder 1400 and trimmer1402. Tack welder 1400 is positioned to help the laying up ofthermoplastic tows along surface 1304 to form braided layup 1306comprised of thermoplastic plies. Tow 1404 is an example of one of thesethermoplastic tows being fed from a braiding ring or a braider. Tackwelder 1400 is resistively heated and helps tack tow 1404 to braidedlayup 1306.

Trimmer 1402 is used to trim tow 1404. Trimmer 1402 may be, for example,without limitation, a laser trimmer. Conductive component 1308 ispositioned between tow 1404 and braided layup 1306 to absorb the laserenergy emitted by trimmer 1402 and thereby protect braided layup 1306.Conductive component 1308 is thermally conductive in these examples.

The illustrations in FIGS. 3-14 are not meant to imply physical orarchitectural limitations to the manner in which an illustrativeembodiment may be implemented. Other components in addition to or inplace of the ones illustrated may be used. Some components may beoptional.

The different components shown in FIGS. 3-14 may be illustrativeexamples of how components shown in block form in FIGS. 1-2 may beimplemented as physical structures. Additionally, some of the componentsin FIGS. 3-14 may be combined with components in FIGS. 1-2, used withcomponents in FIGS. 1-2, or both.

FIG. 15 is a flowchart of a process for forming a composite structure inaccordance with an example embodiment. Process 1500 illustrated in FIG.15 may be performed using, for example, system 113 described in FIG. 1to form composite structure 101. In some examples, consolidation setup300 from FIGS. 3-11 is used to form composite structure 101.

Process 1500 begins by building a stackup that comprises a bladderhaving a plurality of recessed portions, a plurality cauls within theplurality of recessed portions, a plurality of overbraided thermoplasticmembers, a plurality of stringer bladders, and an overbraidedthermoplastic skin, the stackup being positioned between an innertooling and an outer tooling (operation 1502). The stackup, the innertooling, and the outer tooling may be implemented in a manner similarto, for example, stackup 112, inner tooling 108, and outer tooling 110,respectively, in FIG. 1 or stackup 306, inner tooling 304, and outertooling 308, respectively, in FIGS. 3-8.

In some cases, with respect to operation 1502, the stackup is built overthe inner tooling component by component. The outer tooling is thensecured over the stackup. In other cases, the stackup is pre-built andthen positioned over the inner tooling prior to the outer tooling beingpositioned over the stackup.

Thereafter, a load constraint is positioned around the outer toolingsuch that the inner tooling, the stackup, the outer tooling, and theload constraint form a consolidation setup (operation 1504). Theconsolidation setup is heated inductively to consolidate the pluralityof overbraided thermoplastic members to the overbraided thermoplasticskin, thereby forming a composite structure (operation 1506), with theprocess terminating thereafter. In particular, operation 1506 results inthe formation of an integrated composite structure.

In some illustrative examples, operation 1506 may be performed byheating, inductively, a first smart susceptor located between the innertooling and the stackup and a second smart susceptor located between theouter tooling and the stackup to cause consolidation of the plurality ofoverbraided thermoplastic members to the overbraided thermoplastic skin.This process forms a plurality of fuselage stringers integrated with acircumferential skin. The plurality of overbraided thermoplastic membersform the fuselage stringers and the overbraided thermoplastic skin formsthe circumferential skin form a composite fuselage structure, such ascomposite fuselage structure 102 in FIG. 1.

FIG. 16 is a flowchart of a process for building a stackup in accordancewith an example embodiment. Process 1600 illustrated in FIG. 16 may beperformed to build, for example, stackup 112 described in FIG. 1 orstackup 306 described in FIGS. 3-8. Further, process 1600 may be used toimplement operation 1502 in FIG. 15.

Process 1600 begins by positioning a bladder around a first smartsusceptor that surrounds an inner tooling (operation 1602). The bladdermay be comprised of aluminum. In these illustrative examples, the firstsmart susceptor surround the inner tooling like a liner for the innertooling.

Thereafter, a plurality of cauls is positioned within a plurality ofrecessed portions of the bladder (operation 1604). In these illustrativeexamples, each of the plurality of cauls is comprised of a nickel-ironalloy. In one illustrative example, each of the plurality of cauls iscomprised of an invar alloy (e.g., Invar 52).

A plurality of overbraided thermoplastic members is then positioned overthe plurality of cauls (operation 1606). In particular, each of theplurality of overbraided thermoplastic members is positioned over andwithin the recessed portion of a corresponding one of the plurality ofcauls. Each of the plurality of overbraided thermoplastic members has ashape similar to the shape of the corresponding caul. The cauls helpprovide mechanical strength and rigidity during heating to help maintainthe shape and smoothness of the plurality of overbraided thermoplasticmembers.

Next, a plurality of stringer bladders is positioned over the pluralityof overbraided thermoplastic members (operation 1608). An overbraidedthermoplastic skin is then positioned around the plurality of stringerbladders and plurality of overbraided thermoplastic members such thatthe overbraided thermoplastic skin contacts end sections of theplurality of overbraided thermoplastic members, the overbraidedthermoplastic skin and the plurality of overbraided thermoplasticmembers forming the composite fuselage structure after inductiveconsolidation (operation 1610), with the process terminating thereafter.During the inductive consolidation, the overbraided thermoplastic skinis consolidated with or integrated with the overbraided thermoplasticmembers. The overbraided thermoplastic skin forms the fuselage skin andthe overbraided thermoplastic members form the fuselage stringers forthe composite fuselage structure.

FIG. 17 is a flowchart of a process for building a system that includesa consolidation setup in accordance with an example embodiment. Process1700 illustrated in FIG. 17 may be performed to build system 103 thatincludes consolidation setup 104 described in FIG. 1 or system 1000 thatconsolidation setup 300 from FIGS. 3-11.

Process 1700 may begin by positioning a bladder around a first smartsusceptor that surrounds an inner tooling (operation 1702). The innertooling includes a plurality of induction coils embedded within theinner tooling. The inner tooling may be supported by a supportstructure. In these examples, the inner tooling has a circumferentialshape (e.g., a cylindrical or near-cylindrical shape, a taperedcylindrical shape, a conical shape, etc.). In one illustrative example,the inner tooling is shaped such that any given cross-section along alongitudinal axis of the inner tooling has a substantially circular(circular or near-circular) shape.

In operation 1702, the bladder may be an aluminum bladder that has aplurality of recessed portions. The bladder may be positioned around thefirst smart susceptor to surround the first smart susceptor, and therebythe inner tooling.

Cauls are positioned within the recessed portions of the bladder(operation 1704). In operation 1704, the cauls may be comprised of anickel-iron alloy, such as an invar alloy. Each caul is shaped tosubstantially conform to or match the shape of the correspondingrecessed portion of the bladder within which that caul is positioned. Inone illustrative example, the recessed portion of the bladder, andthereby the caul, has an upside-down hat shape.

Overbraided thermoplastic members are then positioned over the cauls(operation 1706). In operation 1706, the overbraided thermoplasticmembers are shaped to substantially conform to or match the cauls.Thereafter, stringer bladders are positioned over the plurality ofoverbraided thermoplastic members (operation 1708). The stringerbladders are shaped to nest within the recessed portions or open spacesdefined by the overbraided thermoplastic members. These stringerbladders may be comprised of aluminum in these illustrative examples.

The stringer bladders are surrounded with an overbraided thermoplasticskin such that the bladder, the cauls, the overbraided thermoplasticmembers, the stringer bladders, and the overbraided thermoplastic skintogether form a stackup (operation 1710). In operation 1710, theoverbraided thermoplastic skin contacts at least portions of theoverbraided thermoplastic members. These portions may be the flangedsections of the overbraided thermoplastic members.

A second smart susceptor is then positioned around the overbraidedthermoplastic skin (operation 1712). Outer tooling is positioned aroundthe second smart susceptor to form a consolidation setup (operation1714). Similar to the inner tooling, the outer tooling includes aplurality of induction coils embedded within the outer tooling. A loadconstraint is then used to secure the outer tooling, the stackup, andthe inner tooling (operation 1716).

Pressurization tubes are inserted through the bladder and the stringerbladders (operation 1718), with the process terminating thereafter. Asone illustrative example, one pressurization tube may be insertedthrough a channel in the bladder, while multiple other pressurizationtubes may be inserted through the stringer bladders (e.g., a singlepressurization tube per stringer bladder). Thus, the consolidation setupincludes the inner tooling, the stackup, the outer tooling, the loadconstraint, and the pressurization tubes. In other illustrativeexamples, the pressurization tubes may be considered separate from theconsolidation setup.

Thereafter, first induction coils embedded in the inner tooling andsecond induction coils embedded in the outer tooling are connected viaconnector devices (operation 1720). These connector devices may take theform of, for example, knife switch connectors. The ends of the stackupare capped using plugs (operation 1722). The plugs are located andsecured using end tooling (operation 1724), with the process terminatingthereafter.

FIG. 18 is a flowchart of a process for building a system to form acomposite fuselage structure in accordance with an example embodiment.Process 1800 illustrated in FIG. 18 may be performed to build system 113described in FIG. 1.

Process 1800 may begin by building a consolidation setup (operation1802). Operation 1802 may be performed using, for example, process 1700in FIG. 17. For example, the consolidation setup built in operation 1802that includes an inner tooling embedded with first induction coils, anouter tooling embedded with second induction coils, a first smartsusceptor, a second smart susceptor, and a stackup positioned betweenthe first smart susceptor and the second smart susceptor, the stackupincluding a plurality of overbraided thermoplastic members and anoverbraided thermoplastic skin.

Next, the consolidation setup is heated inductively using the firstinduction coils, the second induction coils, the first smart susceptor,and the second smart susceptor to thereby consolidate the overbraidedthermoplastic skin with the plurality of overbraided thermoplasticmembers to form the composite fuselage structure (operation 1804), withthe process terminating thereafter.

FIG. 19 is a flowchart of a process for inductively consolidating anoverbraided thermoplastic skin with overbraided thermoplastic members toform a composite fuselage structure in accordance with an exampleembodiment. Process 1900 illustrated in FIG. 19 may be performed toinductively consolidate, for example, overbraided thermoplastic skin 210with overbraided thermoplastic members 206 from FIG. 2. Further, process1900 may be implemented using system 103, which includes consolidationsetup 104 that includes stackup 112, as described in FIG. 1-2.

Process 1900 begins by connecting first induction coils embedded in theinner tooling of a consolidation setup with second induction coilsembedded in the outer tooling of the consolidation setup (operation1902). Operation 1902 may be performed using connector devices such asconnector devices 107 in FIG. 1. In one or more illustrative examples,the first induction coils and the second induction coils may beconnected to ultimately form an annular-shaped solenoid coil.

Thereafter, a selected amount of pressure is applied to the bladder inthe consolidation setup (operation 1904). For example, in operation1904, a pressurization system may be connected to the bladder and mayuse inert gas to apply the pressure. In one illustrative example, thepressurization system pressurization tube located within the bladder orto a channel that extends through the bladder. The pressurization systemmay use inert gas to apply the pressure. In operation 1904, the amountof pressure applied may be small (e.g., about 15 psi).

The first induction coils and the second induction coils are energizedto heat the first smart susceptor and the second smart susceptor in theconsolidation setup and thereby heat the thermoplastic material in theconsolidation setup to within selected tolerances of a selectedtemperature (operation 1906). The selected temperature may be, forexample, a temperature above 350 degrees Fahrenheit. In operation 1906,the thermoplastic material may be the overbraided thermoplastic skin andthe overbraided thermoplastic members of the stackup that will form thefuselage skin and fuselage stringers, respectively, of the compositefuselage structure.

Pressure is applied via the bladder and the stringer bladders (operation1908). Operation 1908 may be performed by, for example, using thepressurization system to apply about pressure of about 250 psi to helpsmooth out the thermoplastic material. Operation 1908 is the step atwhich inductive consolidation of the overbraided thermoplastic skin tothe overbraided thermoplastic members occurs and a composite fuselagestructure is formed. This composite fuselage structure may be, forexample, a fuselage barrel section. The temperature of the thermoplasticmaterial is then reduced (operation 1910). The pressure is reduced whenthe temperature has reached below a selected threshold (operation 1912).For example, in operation 1912, the pressure may be reduced to about 15psi once the temperature has dropped below about 300 degrees Fahrenheit.

Thereafter, the composite fuselage structure is unloaded (operation1914). A vacuum is applied to the bladder to create a gap between thecomposite fuselage structure and the inner tooling of the consolidationsetup (operation 1916). The outer tooling of the consolidation setup isremoved, allowing the composite fuselage structure to be removed fromthe inner tooling (operation 1918), with the process terminatingthereafter.

In other illustrative examples, process 1900 includes additionaloperations for customizing the composite fuselage structure once thecomposite fuselage structure has been removed from the inner tooling.For example, cutouts may be added to the composite fuselage structureand other components may be added to the composite fuselage structure.In one illustrative example, window belt cutouts are added. In otherexamples, fuselage and window frames are added using induction joiningor induction welding techniques. Induction joining or induction weldingmay also be used to add parts such as, for example, without limitation,shear ties, systems brackets, antenna reinforcements, service panreinforcements, other types of parts, or a combination thereof, to thecomposite fuselage structure.

FIG. 20 is a flowchart for forming a composite structure in accordancewith an example embodiment. Process 2000 illustrated in FIG. 20 may beperformed to form a composite structure such as composite structure 101in FIG. 1.

Process 2000 begins by holding an inner tooling, a stackup, and an outertooling in place together using a load constraint (operation 2002). Abladder and a plurality of stringer bladders in the stackup arepressurized to cause expansion of the bladder and the plurality ofbladders, thereby pushing together the overbraided thermoplastic skinand the plurality of overbraided thermoplastic members (operation 2004).

Thereafter, an overbraided thermoplastic skin and a plurality ofoverbraided thermoplastic members are co-consolidated in the stackupwhile the bladder and the plurality of stringer bladders are pressurizedto form the composite structure (operation 2006), with the processterminating thereafter. The pressurization provided in operation 2004ensures that co-consolidation of the overbraided thermoplastic skin andthe plurality of overbraided thermoplastic members occurs evenly andsmoothly.

FIG. 21 is a flowchart for forming a composite fuselage structure inaccordance with an example embodiment. Process 2100 illustrated in FIG.21 may be performed to form a composite structure such as compositestructure 101 in FIG. 1.

Process 2100 begins by expanding a bladder and a plurality of stringerbladders in a stackup to place fibers in an overbraided thermoplasticskin and a plurality of overbraided thermoplastic members in tension(operation 2102). Operation 2102 may be performed by, for example,pressurizing the bladder and the plurality of stringer bladders. In someexamples, the bladder and the stringer bladders are pressurized usingpressurization tubes through which inert gas flows. The pressurizationtubes may be expanded via the addition of inert gas, which may lead toexpansion of the bladder and stringer bladders.

The stackup is heated to melt the overbraided thermoplastic skin and theplurality of overbraided thermoplastic members (operation 2104).Operation 2104 may be performed using induction-based smart susceptorheating. The overbraided thermoplastic skin and the plurality ofoverbraided thermoplastic members are then joined together while theoverbraided thermoplastic skin and the plurality of overbraidedthermoplastic members are melted (operation 2106). The stackup is cooledsuch that the overbraided thermoplastic skin and the plurality ofoverbraided thermoplastic members form an integrated structure that isthe composite fuselage structure (operation 2108), with the processterminating thereafter.

FIG. 22 is a flowchart for forming a composite structure in accordancewith an example embodiment. Process 2200 illustrated in FIG. 22 may beperformed to form a composite structure such as composite structure 101in FIG. 1.

Process 2200 begins by building a stackup comprising a plurality ofoverbraided thermoplastic members and an overbraided thermoplastic skin(operation 2202). The stackup is placed between an inner tooling and anouter tooling (operation 2204). The inner tooling, the stackup, and theouter tooling are held in place together using a load constraint, withthe inner tooling, the stackup, the outer tooling, and the loadconstraint forming a consolidation setup (operation 2206). Theconsolidation setup is heated to form the composite structure (operation2208), with the process terminating thereafter.

FIG. 23 is an illustration of a process for forming a compositestructure in accordance with an example embodiment. Process 2300illustrated in FIG. 23 may be performed to form a composite structuresuch as composite structure 101 in FIG. 1.

Process 2300 may include forming a plurality of consolidated overbraidedthermoplastic preforms (operation 2302). The plurality of consolidatedoverbraided thermoplastic preforms may include a plurality ofoverbraided thermoplastic members and an overbraided thermoplastic skin.Further, process 2300 includes co-consolidating the plurality ofconsolidated overbraided thermoplastic preforms in a circumferentialstackup that is circumferentially constrained (operation 2304). Thefibers of the plurality of consolidated overbraided thermoplasticpreforms are tensioned during co-consolidation (operation 2306).

In process 2300, operation 2304 is performed without the use of anautoclave. In operation 2304, bladders are used to react against theouter load constraint and provide the pressure that would have typicallybeen provided using an autoclave. Further, in operation 2304, inductioncoils and smart susceptors are used to provide the heat that would havetypically been provided using an autoclave.

FIG. 24 is an illustration of a process for forming a compositestructure in accordance with an example embodiment. Process 2400illustrated in FIG. 24 may be performed to form a composite structuresuch as composite structure 101 in FIG. 1.

Process 2400 begins by expanding a plurality of stringer bladders in astackup to thereby apply force against a plurality of overbraidedthermoplastic members and an overbraided thermoplastic skin (operation2402). Operation 2402 may be performed by heating the plurality ofstringer bladders and pressurizing the plurality of stringer bladdersvia an inert gas that flows from a plurality of pressurization tubesinto the plurality of stringer bladders. The expansion of the pluralityof stringer bladders tensions the plurality of overbraided thermoplasticmembers and helps resist compressive loading on the plurality ofoverbraided thermoplastic members.

The stackup is constrained via a dielectric material embedded within anon-dielectric material during expansion of the plurality stringerbladders (operation 2404). Operation 2404 may be performed bycompressing the stackup against an outer tooling comprising thedielectric material. The dielectric material is a ceramic material andthe non-dielectric material may be a plurality of induction coils usedfor the heating performed in operation 2402. The non-dielectric materialis constrained via the dielectric material during the expansion of theplurality of stringer bladders (operation 2406).

FIG. 25 is a flowchart of a process for tacking and trimming athermoplastic tow in accordance with an example embodiment. The processillustrated in FIG. 25 may be used to tack and trim the thermoplastictows that ultimately form overbraided thermoplastic skin 210 andoverbraided thermoplastic members 206 in FIG. 2.

Process 2500 begins by laying up a thermoplastic tow received from abraiding ring over a braided structure on a surface, a portion of thethermoplastic tow being received over a conductive component (operation2502). The thermoplastic tow may be an overbraided thermoplastic tow.The surface may be formed by at least one of a tooling surface, a caul,a bladder, a stringer bladder, a partially-formed braided layup, apreform, an integrated composite structure, or some other type ofsurface. The braided structure may be, for example, a braided layup ofoverbraided thermoplastic material, a partially-formed braided layup, apreform, an integrated structure made of overbraided thermoplasticmaterial, or some other type of braided structure. In operation 2502,the thermoplastic tow may be positioned over the braided structure beingformed on the surface. The conductive component in operation 2502 may bereferred to as a “shoe.”

A tack welder secured to a support ring is then used to tack weld thethermoplastic tow to the braided structure (operation 2504). Inoperation 2504, the tack welder is resistively heated to ensure eventacking of the thermoplastic tow to the braided structure. A portion ofthe thermoplastic tow is trimmed to thereby trim the thermoplastic towreceived over the braided structure (operation 2506), with the processterminating thereafter. In operation 2506, laser energy is applied tothe portion of the thermoplastic tow supported by a conductive componentto trim the thermoplastic tow. The conductive component absorbs thelaser energy to protect the braided structure below the conductivecomponent.

FIG. 26 is a flowchart of a process for tacking and trimming athermoplastic tow in accordance with an example embodiment. The processillustrated in FIG. 26 may be used to tack and trim the thermoplastictows that ultimately form overbraided thermoplastic skin 210 andoverbraided thermoplastic members 206 in FIG. 2.

Process 2600 begins by laying up a thermoplastic tow received from abraiding system over a braided structure on a surface (operation 2602).The received thermoplastic tow is tack welded to the braided structure(operation 2604). The thermoplastic tow is trimmed by applying laserenergy to a portion of the received thermoplastic tow (operation 2606),with the process terminating thereafter.

Example embodiments of the disclosure may be described in the context ofaircraft manufacturing and service method 2700 as shown in FIG. 27 andaircraft 2800 as shown in FIG. 28. Turning first to FIG. 27, anillustration of an aircraft manufacturing and service method is depictedin accordance with an illustrative embodiment. During pre-production,aircraft manufacturing and service method 2700 may include specificationand design 2702 of aircraft 2800 in FIG. 28 and material procurement2704.

During production, component and subassembly manufacturing 2706 andsystem integration 2708 of aircraft 2800 in FIG. 28 takes place.Thereafter, aircraft 2800 in FIG. 28 may go through certification anddelivery 2710 in order to be placed in service 2712. While in service2712 by a customer, aircraft 2800 in FIG. 28 is scheduled for routinemaintenance and service 2714, which may include modification,reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of aircraft manufacturing and service method 2700may be performed or carried out by a system integrator, a third party,and/or an operator. In these examples, the operator may be a customer.For the purposes of this description, a system integrator may include,without limitation, any number of aircraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of vendors, subcontractors, and suppliers; and anoperator may be an airline, a leasing company, a military entity, aservice organization, and so on.

With reference now to FIG. 28, an illustration of an aircraft isdepicted in which an illustrative embodiment may be implemented. In thisexample, aircraft 2800 is produced by aircraft manufacturing and servicemethod 2700 in FIG. 27 and may include airframe 2802 with plurality ofsystems 2804 and interior 2806. Examples of systems 2804 include one ormore of propulsion system 2808, electrical system 2810, hydraulic system2812, and environmental system 2814. Any number of other systems may beincluded. Although an aerospace example is shown, different illustrativeembodiments may be applied to other industries, such as the automotiveindustry.

Apparatuses and methods embodied herein may be employed during at leastone of the stages of aircraft manufacturing and service method 2700 inFIG. 27. In particular, system 103 from FIGS. 1-2 may be used to formcomposite structure 101 during any one of the stages of aircraftmanufacturing and service method 2700. For example, without limitation,system 103 from FIGS. 1-2 may be used to form composite structure 101during at least one of component and subassembly manufacturing 2706,system integration 2708, routine maintenance and service 2714, or someother stage of aircraft manufacturing and service method 2700. Stillfurther, system 103 from FIGS. 1-2 may be used to form at least aportion of airframe 2802 of aircraft 2800 in FIG. 28. For example,system 103 may be used to form a fuselage barrel section of airframe2802.

In one illustrative example, components or subassemblies produced incomponent and subassembly manufacturing 2706 in FIG. 27 may befabricated or manufactured in a manner similar to components orsubassemblies produced while aircraft 2800 is in service 2712 in FIG.27. As yet another example, one or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized during productionstages, such as component and subassembly manufacturing 2706 and systemintegration 2708 in FIG. 27. One or more apparatus embodiments, methodembodiments, or a combination thereof may be utilized while aircraft2800 is in service 2712 and/or during maintenance and service 2714 inFIG. 27. The use of a number of the different illustrative embodimentsmay substantially expedite the assembly of and/or reduce the cost ofaircraft 2800.

The flowcharts and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatuses and methods in an exampleembodiment. In this regard, each block in the flowcharts or blockdiagrams may represent a module, a segment, a function, and/or a portionof an operation or step.

In some alternative implementations of an example embodiment, thefunction or functions noted in the blocks may occur out of the ordernoted in the figures. For example, in some cases, two blocks shown insuccession may be executed substantially concurrently, or the blocks maysometimes be performed in the reverse order, depending upon thefunctionality involved. Also, other blocks may be added in addition tothe illustrated blocks in a flowchart or block diagram.

As used herein, the phrase “at least one of,” when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used and only one of the items in the list may be needed. Theitem may be a particular object, thing, step, operation, process, orcategory. In other words, “at least one of” means any combination ofitems or number of items may be used from the list, but not all of theitems in the list may be required. For example, without limitation, “atleast one of item A, item B, or item C” or “at least one of item A, itemB, and item C” may mean item A; item A and item B; item B; item A, itemB, and item C; item B and item C; or item A and C. In some cases, “atleast one of item A, item B, or item C” or “at least one of item A, itemB, and item C” may mean, but is not limited to, two of item A, one ofitem B, and ten of item C; four of item B and seven of item C; or someother suitable combination. The description of the different exampleembodiments has been presented for purposes of illustration anddescription, and is not intended to be exhaustive or limited to theembodiments in the form disclosed. Many modifications and variationswill be apparent to those of ordinary skill in the art. Further,different example embodiments may provide different features as comparedto other desirable embodiments. The embodiment or embodiments selectedare chosen and described in order to best explain the principles of theembodiments, the practical application, and to enable others of ordinaryskill in the art to understand the disclosure for various embodimentswith various modifications as are suited to the particular usecontemplated.

What is claimed is:
 1. A method for tacking and trimming a thermoplastictow, the method comprising: laying up a thermoplastic tow received froma braiding system over a braided structure on a surface; and tackwelding the thermoplastic tow to the braided structure; trimming aportion of the thermoplastic tow received over the braided structure byapplying laser energy to trim the portion of the thermoplastic towreceived over the braided structure; and supporting the portion of thetow using a conductive component while applying the laser energy to theportion of the tow.
 2. The method of claim 1, wherein a cross-sectionalshape of the conductive component is wedge-shaped.
 3. The method ofclaim 1, wherein tack welding the thermoplastic tow comprises: tackwelding the thermoplastic tow to the braided structure using a tackwelder secured to a support ring.
 4. The method of claim 1, wherein tackwelding the thermoplastic tow comprises: tack welding the thermoplastictow to the braided structure using a tack welder that is secured to asupport ring that surrounds the surface, wherein the tack welder isresistively heated.
 5. The method of claim 1, wherein the conductivecomponent travels with a braiding ring that provides the thermoplastictow.
 6. The method of claim 1, wherein the braided structure comprises aplurality of thermoplastic plies of overbraided continuous thermoplasticcomposite fibers.
 7. The method of claim 1, wherein applying the laserenergy comprises: absorbing the laser energy using the conductivecomponent to protect the braided structure as the thermoplastic tow istrimmed.
 8. The method of claim 1, wherein laying up the thermoplastictow comprises: laying up the thermoplastic tow over the surface, thesurface being formed by at least one of a tooling surface, a caul, abladder, a stringer bladder, a partially-formed braided layup, apreform, or an integrated composite structure.
 9. The method of claim 1,wherein laying up the thermoplastic tow comprises: laying up thethermoplastic tow to add a localized feature to the braided structure.10. The method of claim 1, wherein the method is used in the assembly ofa portion of an aircraft composite barrel section.
 11. The method ofclaim 1, wherein the laying-up, the tack welding, and the trimming areperformed by a tow tacking and trimming apparatus comprising: atacking-trimming system for use in the tack welding and the trimming;and a support system to which the tacking-trimming system is attached,the support system sized and shaped to operatively place thetacking-trimming system relative to a cylindrical thermoplastic stackup.12. The method of claim 11, wherein the support system comprises: asupport ring sized and shaped to fully surround a surface that iscircumferential, wherein the tacking-trimming system is secured to thesupport ring.
 13. The method of claim 11, wherein the tacking-trimmingsystem comprises: a tack welder secured to a portion of the supportsystem, wherein the tack welder is resistively heated.
 14. The method ofclaim 11, wherein the tacking-trimming system comprises: a trimmersecured to a portion of the support system, wherein the trimmer useslaser energy to trim the thermoplastic tow.
 15. The method of claim 14further comprising: the conductive component positioned between thebraided structure and the thermoplastic tow.
 16. The method of claim 15,wherein a cross-sectional shape of the conductive component iswedge-shaped.
 17. The method of claim 15, wherein the conductivecomponent is thermally conductive and used to absorb the laser energyemitted by the trimmer to protect the braided structure.
 18. The methodof claim 15, wherein the thermoplastic tow is received from a braidingring and is passed over the conductive component.
 19. The method ofclaim 11, wherein the support system travels with a braiding ring thatprovides the thermoplastic tow.
 20. The method of claim 11, wherein thetacking-trimming system is one of a plurality of tacking-trimmingsystems distributed along the support system.
 21. The method of claim11, wherein the braided structure comprises a plurality of thermoplasticplies of overbraided continuous thermoplastic composite fibers.
 22. Amethod for tacking and trimming a thermoplastic tow, the methodcomprising: laying up the thermoplastic tow received from a braidingsystem over a braided structure on a surface; and tack welding thethermoplastic tow received from the braiding system to the braidedstructure; and trimming the thermoplastic tow by applying laser energyto a portion of the thermoplastic tow; wherein trimming thethermoplastic tow comprises: applying the laser energy to the portion ofthe thermoplastic tow supported by a conductive component.
 23. Themethod of claim 22, further comprising: supporting the portion of thethermoplastic tow by the conductive component; wherein applying thelaser energy comprises absorbing the laser energy using the conductivecomponent to protect the braided structure as the thermoplastic tow istrimmed.
 24. The method of claim 22, wherein the conductive componentmoves relative to the braided structure during the laying-up.
 25. Themethod of claim 22, wherein the method is used in the assembly of aportion of an aircraft composite barrel section.
 26. The method of claim22, wherein the laying-up, the track welding, and the trimming areperformed by a tacking-trimming setup comprising: a support ring sizedand shaped to fully surround a surface that is circumferential; atacking-trimming system secured to the support ring for use in tackingthe thermoplastic tow to the braided structure, wherein thetacking-trimming system comprises: a tack welder secured to a portion ofthe support ring, wherein the tack welder is resistively heated; and atrimmer secured to a portion of the support ring, wherein the trimmeruses laser energy to trim the thermoplastic tow; and the conductivecomponent positioned between the braided structure and the thermoplastictow.
 27. The method of claim 26, wherein a cross-sectional shape of theconductive component is wedge-shaped and thermally conductive to absorbthe laser energy emitted by the trimmer to protect the braided structureduring trimming of the thermoplastic tow.
 28. The method of claim 27,wherein the tacking-trimming system is one of a plurality oftacking-trimming systems distributed along the support ring.
 29. Themethod of claim 26, wherein the braided structure comprises a pluralityof thermoplastic plies of overbraided continuous thermoplastic compositefibers.
 30. The method of claim 26, wherein the surface is formed by atleast one of a tooling surface, a caul, a bladder, a stringer bladder, apartially-formed braided layup, a preform, or an integrated compositestructure.